KR101233472B1 - Cross-flow fan and air conditioner equipped with same - Google Patents

Abstract

The cross flow fan is provided with the vane comprised by the plate-shaped vanes 42. As shown in FIG. The blade | wing 42 is inclined so that the outer edge 42a of this blade | wing 42 may be located ahead of the rotational direction of the blade wheel 41 rather than the inner edge 42d. The side surface located in front of the rotational direction of the blade | wing 42 among the both side surfaces of this blade | wing 42 comprises the pressure surface 42p, and the side surface located in the back of this rotational direction comprises the negative pressure surface. At the outer edge 42a of the blade 42, a plurality of cutouts 42b are formed at predetermined intervals along the rotation axis of the vane, and a basic portion 42c is provided between two adjacent cutouts 42b. Formed. The blade thickness L2 near the bottom part 42y of the notch 42b is smaller than the blade thickness of the basic shape part 42c adjacent to this notch 42b.

Description

CROSS-FLOW FAN AND AIR CONDITIONER EQUIPPED WITH SAME}

The present invention relates to a cross flow fan and an air conditioner having the same.

As a blower used for the indoor unit of a wall-mounted air conditioner, a cross flow fan is known. 22 shows an example of a crossflow fan. As shown in FIG. 22, the cross flow fan 104 is a cross flow blower (perfusion blower), and is provided with the vane | wheel 141 comprised by the many blade | wing (wings) 142. As shown in FIG. These wings 142 are inclined so that their outer edges are located in front of the rotational direction Z1 of the vanes 141 rather than the inner edges, and are so-called forward wings. As the vanes 141 are rotated in the rotational direction Z1 by the vibration motor, the air stream X (that is, the roughened air streams) cooled or heated in the indoor unit 1 in the air conditioner is rotated by the vanes 141. On the plane perpendicular to the line Z, the vanes 141 are pulled out to be traversed and blown into the room.

In the vanes of such a cross flow fan, noise is generated when air passes through the vanes forming the vanes. For the purpose of reducing this noise with a simple configuration, a cross flow fan having a plurality of cutouts with a predetermined interval at the edge of the blade has been proposed (see Patent Document 1, for example). 23 and 24 show the vanes of vanes in such a cross flow fan. As shown to FIG. 23 and FIG. 24, the some notch 242b is formed in the outer edge 242a of the plate-shaped wing | wing 242 at predetermined intervals. Between the adjacent notches 242b, the basic shape part 242c is formed. As shown in FIG. 25, the bottom part 242y of the notch 242b comprised in this way is extended in the direction substantially perpendicular to the both sides of the blade | wing 242, and the wing thickness near the bottom part 242y of the notch 242b. L6 is equal to the blade thickness L5 of the basic shape portion 242c. As described above, by forming the plurality of cutouts 242b in the blade 242, the wakes (not shown) generated in the blowout region M of the crossflow fan 204 are reduced, that is, The noise of the crossflow fan 204 can be effectively reduced by changing a simple shape with respect to the blade | wing 242. As shown in FIG.

Patent Document 1: Japanese Unexamined Patent Publication No. 2006-125390

As described in Patent Document 1, the noise can be effectively reduced by a simple configuration in which a cutout is formed at the edge portion of the blade. However, when adopting such a configuration, there is a problem that the air resistance to the rotation of the vanes 241 increases. Specifically, as shown in FIG. 26, in the case where the notch 242b is formed at the outer edge 242a of the wing 242, when the vanes 241 rotate, approximately both sides of the wing 242 are roughly formed. The airflow X collides with the bottom 242y of the notch 242b extending in the vertical direction. For this reason, compared with the case where notch is formed in the outer edge 242a, in the suction area | region N of the crossflow fan 204, the airflow X collides with the rotation of the vane | wheel 241. Air resistance increases. As a result, in order to ensure the airflow amount by the crossflow fan 204, the output of the electric motor which drives this crossflow fan 204 must be increased.

This invention is made | formed in view of such a situation, and the objective is to provide the crossflow fan which can suppress the increase of the output of the electric motor which drives a crossflow fan, and the air conditioner provided with this.

MEANS TO SOLVE THE PROBLEM In order to solve the said problem, according to one aspect of the present invention, a plurality of support plates positioned on the rotation axis of the vanes and a plurality of plate-shaped wings provided on the periphery of the support plate and extending in parallel with the rotation axis And a vane configured by the vanes, wherein the vanes are inclined such that their outer edges are located in the front of the vane's rotational direction rather than the inner edges, and the side surfaces located in front of the vanes' rotational direction among both side surfaces of the vane In the cross flow fan which comprises a pressure surface and the side located in the back of the said rotation direction comprises a negative pressure surface, in the at least one of the inner side edge and the outer edge of the said blade, the several notch is the rotation axis of the said blade wheel. In addition to being formed at a predetermined interval along the basic shape between the two adjacent cutouts, Group cutouts wing thickness of the bottom vicinity of the wing section than the thickness of said basic shape is also provided with a small cross-flow fan adjacent gyeole.

According to this configuration, a plurality of cutouts are formed at predetermined intervals along at least one of the inner and outer edges of the vanes at predetermined intervals along the rotation axis of the vane, and a basic shape portion is formed between two adjacent cutouts. Therefore, the noise can be effectively reduced with a simple configuration. In addition, since the wing thickness near the bottom of a notch is smaller than the wing thickness of a base-shaped part, the collision loss at the time of inflow of airflow into a cutout part can be reduced. As a result, the increase of the output of the electric motor which drives a crossflow fan can be suppressed. In the above, the "predetermined interval" may be a constant interval, or the interval may be changed by the position of the blade in the longitudinal direction.

In the present invention, the cutout is formed at an outer edge of the blade, and a plurality of grooves extending inward from the outside of the blade are formed on either one of the pressure surface and the negative pressure surface to correspond to the cutout, respectively. The wing thickness in the vicinity of the bottom of the notch is smaller than the wing thickness of the basic shape portion adjacent to the notch, and the wing thickness of the portion corresponding to the groove in the wing is the inner edge of the wing from the bottom of the notch. It is preferable to gradually increase as it faces.

According to this structure, the part corresponding to a groove | channel in a blade | wing is formed so that the blade thickness may become large gradually from blade | wing thickness as it goes to the inner edge of a blade | wing from the bottom of a notch. Therefore, the part located inward of the groove and the bottom of the notch in the pressure surface or the negative pressure surface of the blade are smoothly connected by the surface of the groove. Accordingly, the air flow flowing into the notch from the outer circumferential side of the blade on the suction side of the cross flow fan can smoothly flow into the vane along the pressure or negative pressure surface. Therefore, the collision loss at the time of inflow of airflow from the outside of a blade | wing can be reduced. As a result, an increase in the output of the electric motor that drives the cross flow fan can be effectively suppressed due to the formation of cutouts in the blades.

Moreover, in this invention, the said notch is formed in the inner edge of the said wing, and the some groove | channel which extends outward from the inside of the said wing in either one of the said pressure surface and the said negative pressure surface respectively responds to the said notch, respectively. By being formed, the wing thickness in the vicinity of the bottom part of the said notch becomes smaller than the wing thickness of the said basic-shape part adjacent to this notch, and the wing thickness of the part corresponding to the said groove | channel in the said wing | blade is made from the bottom of the said notch of the said wing | blade. It is also possible to adopt a configuration that gradually grows toward the outer edge.

According to this structure, the part corresponding to a groove | channel in a blade | wing is formed so that the blade thickness may gradually become large from blade | wing thickness as it goes to the outer edge of a blade | wing from the bottom of a notch. Therefore, the part located outside the groove and the bottom of the notch in the pressure surface or the negative pressure surface of the blade are smoothly connected by the surface of the groove. Therefore, the air flow which flows into the notch from the inside of a blade | wing can flow out smoothly from the inside of vane along a pressure surface or a negative pressure surface. Therefore, the collision loss at the time of inflow of airflow from the inside of a blade | wing can be reduced. As a result, an increase in the output of the electric motor that drives the cross flow fan can be effectively suppressed due to the formation of cutouts in the blades. In addition, when grooves corresponding to cutouts and cutouts are formed at both the outer edge and the inner edge of the blade, the noise is more effectively compared with the case where the cutout is provided only at one of the outer edge and the inner edge of the blade. The collision loss can be reduced while reducing, and the increase of the output of the electric motor which drives a crossflow fan can also be suppressed.

Moreover, in this invention, the said notch is V-shaped from the negative pressure surface and the pressure surface of the said blade | wing, and the said groove gradually becomes shallow as it goes to both sides from the center part in the width direction, It is preferable that the blade thickness is continuously formed as the main shape portion adjacent to the groove is changed.

According to this structure, since the notch is V-shaped from the negative pressure surface and the pressure surface of a blade | wing, compared with the case where the notch is formed in a spherical form, the pressure area of a blade | wing can be ensured. Moreover, the groove | channel corresponding to a notch becomes shallow gradually gradually toward the both sides from the center part in the width direction, and is formed so that the blade thickness may change continuously as it goes to the said basic shape part adjacent to this groove | channel from the said groove | channel. . For this reason, compared with the case where a step is not formed in the boundary part of the groove | channel corresponding to a notch and the basic shape part adjacent to this groove in the longitudinal direction of a blade | wing, and a step is formed in the boundary part of a groove | channel and the basic shape part, The airflow can be prevented from being disturbed, and the increase in the output of the electric motor that drives the crossflow fan can be further suppressed.

Moreover, in this invention, it is preferable that the said pressure surface is a state of basic shape, and the said groove | channel is formed in the said negative pressure surface.

According to this structure, since the pressure surface is a basic shape and the groove | channel corresponding to a notch is formed in the negative pressure surface, compared with the case where the groove | channel corresponding to a notch is formed in a pressure surface, the pressure given to airflow Can be increased.

Further, in the present invention, a turbulent boundary layer for suppressing the separation of the air flow flowing into the blade from the blade by transitioning the boundary layer of the air flow formed near the negative pressure surface from laminar flow to turbulent flow on the negative pressure surface of the blade. It is preferable that a control structure is formed.

According to this configuration, a turbulent boundary layer control structure (for example, dimples, grooves, and rough surfaces) is provided on the negative pressure surface of the blade to prevent the air flow flowing into the blade from being separated from the blade by changing the boundary layer of the air flow from the laminar flow to the turbulent flow. Etc.), the boundary layer on the negative pressure surface of the blade can be transferred from laminar flow to turbulent flow. Therefore, the deceleration of the flow of air in the boundary layer is reduced, and the flow of air flowing into the blade can be prevented from peeling from the blade. In particular, when cutouts are formed at the edges of the blades, the gas of the two-dimensional flows (that is, the flows with the three-dimensionality) flows into the blades, so that turbulences such as dimples and irregular roughness whose cross-sectional shape changes. By providing a boundary layer control structure, peeling of the flow of the air which flows into a blade | wing can be suppressed effectively. As a result, the pressure resistance which acts on a blade | wing can be made small, and the output of the electric motor which drives a crossflow fan can be reduced compared with the case where the turbulent boundary layer control structure is not provided.

Moreover, in this invention, it is preferable that the said turbulence boundary layer control structure is provided in the said basic shape part formed between the said notches.

According to this structure, since the turbulence boundary layer control structure is provided in the basic shape part formed between notches, for example, compared with the case where dimples or grooves are formed as a turbulence boundary layer control structure in the groove | channel corresponding to a notch, It is easy to form dimples or grooves having a desired depth. That is, since the wing | blade thickness of a basic shape part is large compared with a groove | channel, the depth of the dimple and groove | channel as a turbulent boundary layer control structure can be easily ensured.

Moreover, in this invention, it is preferable that the said turbulence boundary layer control structure is a dimple.

According to this configuration, since the turbulent boundary layer control structure for transitioning the boundary layer from laminar flow to turbulent flow is a dimple, the turbulent boundary layer control structure suppresses the peeling of the gas flowing into the blade as compared with the case where the groove is formed extending in the direction in which the gas flows. The effect can be made high. That is, if the turbulent boundary layer control structure is a dimple, the shear layer generated at the bottom of the boundary layer can be reduced by transitioning the boundary layer from laminar flow to turbulent flow and generating a secondary flow in the dimple. Therefore, the flow of the air which flows into a blade | wing can be suppressed more from peeling from a blade | wing.

Moreover, in this invention, the said dimple is formed in multiple numbers along the direction through which a gas flows in the vicinity of the outer edge of this wing | blade in the negative pressure surface of the said wing, The depth of the said some dimples is the outer edge of the said wing | blade. It is preferred to become shallow as it faces from the inner edge.

According to this structure, since the depth of the some dimple formed in the vicinity of the outer edge of a blade | wing becomes shallow as it goes to the inner edge, dimples formed apart from the outer edge of a blade | wing of a plurality of dimples are near the outer edge. Compared to the dimples formed in the, it has a small depth. By varying the depths of the plurality of dimples in this way, it is possible to suppress the loss due to the flow of secondary air in the dimples formed away from the outer edges, where the effect of suppressing the development of the boundary layer is small. Therefore, compared with the case where the several dimples have the same depth, the output of the electric motor which drives a crossflow fan can be reduced. In addition, among the plurality of dimples formed in the vicinity of the outer edge, a configuration in which only a part thereof becomes shallow as it faces the inner edge from the outer edge may be adopted, and the constitution in which all of these dimples become shallow as the inner edge is directed from the outer edge thereof. You may employ | adopt.

Moreover, the said dimple is formed in multiple numbers along the direction which a gas flows in the vicinity of the inner edge of this wing | blade in the negative pressure surface of the said wing, The depth of the said some dimples faces an outer edge from the inner edge of the said wing | blade. It is also possible to adopt a configuration that becomes shallower.

According to this structure, since the depth of the some dimple formed in the vicinity of the inner edge of a blade | wing becomes shallow as it goes to the outer edge, the dimple formed apart from the inner edge of a blade | wing of the plurality of dimples is near the inner edge. Compared to the dimples formed in the, it has a small depth. By varying the depths of the plurality of dimples in this way, it is possible to suppress the loss due to the flow of secondary air in the dimples formed away from the inner edge where the effect of suppressing the development of the boundary layer is small. Therefore, compared with the case where the several dimples have the same depth, the output of the electric motor which drives a crossflow fan can be reduced. Moreover, the structure which becomes shallow as a part only moves toward an outer edge from an inner edge among the some dimples provided in the vicinity of an inner edge may be employ | adopted, and the structure which becomes shallow as all of these dimples toward an outer edge from an inner edge You may employ | adopt.

Moreover, according to this invention, the air conditioner provided with the crossflow fan which has the above-mentioned structure is provided.

According to the present invention, a plurality of cutouts are formed at predetermined intervals along at least one of the inner and outer edges of the vanes at predetermined intervals along the axis of rotation of the vanes, and a basic shape is formed between two adjacent cutouts. Therefore, the noise can be effectively reduced with a simple configuration. In addition, since the wing thickness near the bottom of a notch is smaller than the wing thickness of a base-shaped part, the collision loss at the time of inflow of airflow into a cutout part can be reduced. As a result, the increase of the output of the electric motor which drives a crossflow fan can be suppressed.

BRIEF DESCRIPTION OF THE DRAWINGS The schematic block diagram which shows the indoor unit of the air conditioner provided with the crossflow fan which concerns on 1st Embodiment of this invention.
2 is a perspective view showing a crossflow fan according to this embodiment.
(A), (b) is a perspective view which shows the blade | wing of the vane which comprises the crossflow fan which concerns on this embodiment.
4 is a view for explaining a blade with a notch according to this embodiment.
(A) is sectional drawing along the 5a-5a line | wire of FIG. 4, FIG. 5 (b) is sectional drawing along the 5b-5b of FIG.
6 is a cross-sectional view taken along line 6-6 of FIG.
7 is a view for explaining the inflow of airflow into the cutout portion according to this embodiment.
8 is a graph for explaining the effect of the crossflow fan according to this embodiment.
Fig.9 (a), (b) is a perspective view which shows the blade | wing of the vane which comprises the crossflow fan which concerns on 2nd Embodiment of this invention.
10 is a view for explaining a blade with a notch according to this embodiment.
(A) is sectional drawing along the 11a-11a line of FIG. 10, and FIG. 11 (b) is sectional drawing along the 11b-11b line of FIG.
12 is a cross-sectional view taken along the 12-12 line of FIG. 10;
Fig. 13 is a view for explaining the inflow of airflow into the cutout portion according to this embodiment.
14 (a) and 14 (b) are perspective views showing modifications of the vanes of the vanes that constitute the crossflow fan;
Fig. 15 is a diagram for explaining a modification of the blade in which the notches are formed;
FIG. 16 is a cross sectional view along line 16-16 of FIG. 15;
17A and 17B are perspective views showing other modifications of the vanes of the vanes constituting the crossflow fan according to the embodiment of the present invention.
18 is a view for explaining a wing according to this modification.
FIG. 19 is a sectional view along line 19-19 of FIG. 18;
20 is a view for explaining the effect of dimples formed on the negative pressure surface of the blade according to this modification;
21 is a graph for explaining the effect of the crossflow fan according to this modification.
22 is a diagram for explaining a conventional cross flow fan.
23 (a) and 23 (b) are perspective views showing vanes of vanes constituting a conventional cross flow fan;
24 is a view for explaining a wing in which a conventional notch is formed.
(A) is sectional drawing along the 25a-25a line of FIG. 24, and FIG. 25 (b) is sectional drawing along the 25b-25b line of FIG.
Fig. 26 is a diagram for explaining a conventional cross flow fan.

(First Embodiment) Fig.

EMBODIMENT OF THE INVENTION Hereinafter, 1st Embodiment of this invention is described, referring FIGS. 1-8.

As shown in FIG. 1, the air conditioner which concerns on this embodiment is equipped with the wall-mounted indoor unit 1, This indoor unit 1 is provided in the main body casing 2 and the main body casing 2; A heat exchanger 3 and a cross flow fan 4 are provided. The cross flow fan 4 is provided with the vane 41 which has a plate-shaped vane (wing | blade) 42, and this vane 41 is driven by an electric motor (not shown), and is made into air. Is pumped from the suction region N to the extraction region M. FIG.

The air intake port 21 is provided in the upper surface and the front surface (left side of the figure) of the main body casing 2, and the air outlet 22 is provided in the lower surface of the main body casing 2. As shown in FIG. The air blower outlet 22 is provided with the vertical blade | wing 23 and the horizontal blade | wing 24 for adjusting the direction of the air blown out from this air blower outlet 22. As shown in FIG.

In the inner side of the main body casing 2, the guide part 25 is formed in the vicinity of the extraction area | region M of the crossflow fan 4, and this guide part 25 is attached to the crossflow fan 4, It forms the flow path of air blown out by it. The backflow prevention tongue 26 is formed in the air outlet 22, and the backflow prevention tongue 26 separates the blowout area M and the intake area N to prevent backflow of the blown air. .

The heat exchanger 3 is located between the air intake port 21 and the vane 41, and is comprised by the front heat exchange part 3a and the back heat exchange part 3b. The front heat exchange part 3a is provided in the main body casing 2 near the front surface, and the back heat exchange part 3b is provided continuously in the upper end of the front heat exchange part 3a, and the main body casing 2 ) Is installed in the vicinity of the rear surface.

By the above-described configuration, when the vanes 41 of the cross flow fan 4 are driven by an electric motor, indoor air is sucked from the air intake port 21 into the main body casing 2. After the air is cooled or heated by passing through the heat exchanger 3, the air exits the crossflow fan 4 and is blown out of the air blower outlet 22 into the room. As a result, the conditioned air is blown into the room.

As shown in FIG. 2, the vane 41 of the crossflow fan 4 supports many plate-shaped vanes 42 and such vanes 42, and is formed on the rotation axis A1 of the vane 41. It consists of the circular support plate 43 located in this, and the input shaft 44 connected to the electric motor, and extended along the rotation axis A1. These support plates 43 are provided in parallel at predetermined intervals along the rotation axis A1 of the vanes 41, that is, the longitudinal direction of the vanes 42. The blade | wing 42 is fixed between the outer periphery 43a of the support plate 43, and is provided between two adjacent support plates 43 so that it may extend in parallel with the rotation axis A1.

Hereinafter, the structure of the blade | wing 42 is demonstrated in detail with reference to FIG. 3 and FIG. As shown in FIG. 2, the blade | wing 42 has predetermined blade angle so that the outer edge 42a of this blade | wing 42 is located in front of the rotation direction Z1 of the blade wheel 41 rather than the inner edge 42d. It is inclined and is a so-called forward wing. As shown to FIG.2 and FIG.3, the side surface located in front of the rotation direction Z1 among the both side surfaces of the blade | wing 42 comprises the pressure surface 42p, and the side surface located behind the rotation direction Z1 has a negative pressure. The surface 42q is comprised. Moreover, the blade 42 is curved so that the outer edge 42a of this blade 42 may be located ahead of the rotation direction Z1 of the blade wheel 41 rather than the inner edge 42d.

In the outer edge 42a of the blade | wing 42, the some notch 42b is formed along the rotation axis A1 of the blade wheel 41 at predetermined intervals. These notches 42b are formed so as to form a V shape as seen from the negative pressure surface 42q and the pressure surface 42p of the blade 42. The basic shape part 42c which has the curved basic shape of the blade | wing 42 is formed between two adjacent notch 42b.

The space | interval of two adjacent notch 42b may be set to a fixed value, or may be set to another value. For example, as shown in FIG.3 and FIG.4, since the edge part 6a of the blade | wing 42 in the rotation axis A1 is the vicinity of the support plate 43, the blade | wing 42 in the rotation axis A1 is shown. The flow velocity of the air stream X flowing through the end portion 6a is slower than that of the central portion 6b. In this embodiment, the space | interval of the notch 42b in the edge part 6a of the blade | wing 42 is set larger than the space | interval of the notch 42b in the center part 6b of the blade | wing 42. As shown in FIG. Thereby, the pressure area of the edge part 6a of the blade | wing 42 can be ensured.

The notches 42b may all be formed in the same size, but may be latched in different sizes depending on the position on the rotation axis A1. In this embodiment, the notch 42b of the edge part 6a of the blade | wing 42 in rotation axis A1 is smaller than the notch 42b of the center part 6b of the blade | wing 42 in rotation axis A1. Formed. Thereby, the pressure area of the edge part 6a of the blade | wing 42 can be ensured.

As mentioned above, as shown in FIG. 4, the notch 42b is formed in the outer edge 42a of the blade | wing 42 at predetermined intervals, and the some basic shape part 42c is formed between the notch 42b. It is. For this reason, wakes (not shown) generated in the extraction region M of the crossflow fan 4 can be reduced, and noise can be effectively reduced with a simple configuration.

Since the notch 42b is formed like a V shape from the negative pressure surface 42q and the pressure surface 42p of the blade 42, the blade 42 is compared with the case where the notch 42b is formed in a spherical shape. The pressure area of can be secured.

(A) is sectional drawing of the blade | wing 42 along the 5a-5a line | wire of FIG. 4, and FIG. 5 (b) is sectional drawing of the blade | wing 42 along the 5b-5b line | wire of FIG. FIG. 6: is sectional drawing of the blade 42 along the 6-6 line | wire of FIG. As shown to Fig.5 (a), (b), the width | variety of the bottom part 42y of the notch 42b in the thickness direction of the blade | wing 42, ie, the blade thickness L2 near the bottom part 42y, is this notch. It is formed smaller (that is, thinner) than the blade thickness L1 of the basic shape part 42c provided adjacent to 42b.

More specifically, as shown in FIGS. 3 to 6, the pressure surface 42p is in a basic shape, and on the negative pressure surface 42q of the blade 42, from the outside of the blade 42 to the inside. A plurality of extending grooves 42t are formed in correspondence with the notches 42b, respectively. As the groove 42t is formed in the negative pressure surface 42q in this manner, the blade thickness L2 near the bottom 42y of the cutout 42b in the thickness direction of the blade 42 is adjacent to the cutout 42b. It becomes smaller than the blade | wing thickness L1 of the basic shape part 42c. Thereby, the blade thickness L in the cross section along the longitudinal direction of the blade | wing 42 is changing.

By this structure, the blade thickness of the vicinity of the bottom part 42y of the notch 42b can be made small. Therefore, as shown in FIG. 7, the collision loss when the airflow X flows into the notch 42b provided in the outer edge 42a can be reduced.

3 and 5, the portion corresponding to the groove 42t in the blade 42 faces the inner edge 42d of the blade 42 from the bottom 42y of the notch 42b. The blade thickness is formed so as to gradually increase from the blade thickness L. That is, the part located inward of the groove | channel 42t in the negative pressure surface 42q of the blade | wing 42, and the bottom part 42y of the notch 42b are connected smoothly by the surface of the groove | channel 42t.

In addition, as shown in FIG. 6, the groove 42t is formed so that it gradually becomes shallow as it goes to both sides from the center part in the longitudinal direction of the blade 42, ie, the width direction of the groove 42t. In other words, the part corresponding to the groove | channel 42t in the blade | wing 42 is formed so that blade thickness L may become large gradually toward both sides from the center part of the groove | channel 42t. Thereby, in the longitudinal direction of the blade | wing 42, ie, the rotation axis A1 of the blade wheel | wing 41, it is step | step | step in the boundary 42e of the groove | channel 42t and the basic shape part 42c adjacent to this groove | channel 42t. Is not formed, and the blade thickness L continuously changes from the groove 42t toward the basic shape portion 42c adjacent to the groove 42t.

According to the crossflow fan 4 of this embodiment, the following effects can be acquired.

(1) The notch 42b is formed in the outer edge 42a of the blade 42, and the wing thickness L2 near the bottom part 42y of the notch 42b is formed smaller than the wing thickness L1 of the basic-shaped part 42c. I made it. Therefore, in the suction region N of the cross flow fan 42b, the collision loss when the airflow X flows into the notch 42b from the outer side of the blade | wing 42 so that it may resist rotation of the blade wheel 41 is carried out. Can be reduced. As a result, as shown in FIG. 8, the output of the electric motor which drives the crossflow fan 4 can be reduced compared with the output of the conventional electric motor, and the output of the electric motor resulting from notching is formed. The increase of can be suppressed. 8 is a wind-flow-motor output characteristic diagram of the cross flow fan 4 and the conventional cross flow fan 204 according to the present embodiment. In FIG. 8, the solid line shows the airflow-motor output characteristic with respect to the crossflow fan 4 of this embodiment, and the dashed-dotted line shows the airflow-motor output characteristic with respect to the conventional crossflow fan 204. In FIG. 8 represents the air volume, and one division of the horizontal axis is 0.5 m ³ / min. 8 represents the motor input, and one division of the vertical axis is 5W.

(2) The portion of the blade 42 corresponding to the groove 42t faces the inner edge 42d of the blade 42 from the bottom 42y of the notch 42b, so that the blade thickness is the blade thickness. It is formed to gradually increase from L. Therefore, the part located inward of the groove | channel 42t in the negative pressure surface 42q of the blade | wing 42, and the bottom part 42y of the notch 42b are connected smoothly by the surface of the groove | channel 42t. Therefore, the airflow X which flows into the notch 42b from the outer side of the blade | wing 42 can flow smoothly in the vane 41 along the negative pressure surface 42q. Therefore, the collision loss when the airflow X flows into the notch 42b from the outer side of the blade | wing 42 can be reduced. As a result, an increase in the output of the electric motor that drives the crossflow fan 4 can be effectively suppressed due to the formation of cutouts in the blades 42.

(3) The grooves 42t are formed so as to gradually become shallow as they move from the central portion of the grooves 42t in the longitudinal direction of the blade 42, that is, the axis of rotation of the vanes 41. In other words, the part corresponding to the groove | channel 42t in the blade | wing 42 is formed so that blade thickness L may become large gradually toward both sides from the center part of the groove | channel 42t. For this reason, in the longitudinal direction of the blade | wing 42, a step is not formed in the boundary part 42e of the groove | channel 42t, and blade | wing thickness L changes continuously. Therefore, compared with the case where the step | step is formed in the boundary part 42e of the groove | channel 42t and the base-shaped part 42c, it is possible to prevent the airflow X which flows in from the outer side of the blade | wing 42 from being scattered, Increase of the output of the electric motor which drives the flow fan 4 can further be suppressed.

(4) When the pressure surface 42p is in a basic shape, and the groove 42t is formed in the negative pressure surface 42q, a groove corresponding to the cutout 42b is formed in the pressure surface 42p. In comparison with this, the pressure given to the air stream X can be increased.

Moreover, in this embodiment, since the air conditioner is equipped with the crossflow fan 4 which can acquire the effect of said (1)-(4), it obtains the same effect as said (1)-(4). Can be.

(2nd embodiment)

Next, a second embodiment of the present invention will be described. Since the whole structure of the air conditioner which concerns on this embodiment, the structure of a crossflow fan, etc. are the same as that of 1st Embodiment mentioned above, detailed description is abbreviate | omitted here.

In the present embodiment, as shown in Figs. 9 and 10, a plurality of cutouts 42b are formed at predetermined intervals along the rotation axis A1 of the vane 41 at the inner edge 42d of the vane 42. It is. These notches 42b are formed so as to form a V shape as seen from the negative pressure surface 42q and the pressure surface 42p of the blade 42. Between two adjacent notches 42b, the basic shape part 42c which has the basic shape which the blade | wing 42 curved was formed.

The basic shape part 42c is a non-cut part in which a cutout is not formed and is not cut out. The space | interval of two adjacent notch 42b may be set to a fixed value, or may be set to another value.

As mentioned above, as shown in FIG. 13, the notch 42b is formed in the inner edge 42d of the blade | wing 42 at predetermined intervals, and the some basic shape part 42c is formed between the notch 42b. It is. For this reason, wakes (not shown) generated in the suction region N of the crossflow fan 4 can be reduced, and noise can be effectively reduced with a simple configuration.

Since the notch 42b is formed to have a V shape when viewed from the negative pressure surface 42q and the pressure surface 42p of the blade 42, the cutout 42b is formed into a spherical shape, compared to the case where the notch 42b is formed into a spherical shape. The pressure area can be secured.

FIG. 11: (a) is sectional drawing of the blade 42 along the 11a-11a line of FIG. 10, and FIG. 11 (b) is sectional drawing of the blade 42 along the line 11b-11b of FIG. FIG. 12: is sectional drawing of the blade 42 along the 12-12 line of FIG. As shown to Fig.11 (a), (b), the blade thickness L4 of the bottom part 42z of the notch 42b in the thickness direction of the blade | wing 42 is a basic shape formed adjacent to this notch 42b. It is formed smaller than the blade | wing thickness L3 of the part 42c.

More specifically, as shown in FIGS. 9-12, the pressure surface 42p is a state in basic shape, and it extends from the inner side of this blade | wing 42 to the outer side in the negative pressure surface 42q of the blade | wing 42. A plurality of grooves 42t to be formed are respectively formed corresponding to the notches 42b. As the groove 42t is formed in the negative pressure surface 42q in this way, the blade thickness L4 of the bottom portion 42z of the cutout 42b in the thickness direction of the blade 42 is adjacent to the cutout 42b. It becomes smaller than the blade | wing thickness L3 of the shape part 42c. Thereby, the blade thickness L in the cross section along the longitudinal direction of the blade | wing 42 is changing.

By this structure, the blade thickness of the bottom part 42z of the notch 42b can be made small. Therefore, as shown in FIG. 13, the collision loss when the airflow X flows into the notch 42b formed in the inner edge 42d can be reduced.

9 and 11, the portion corresponding to the groove 42t in the blade 42 faces the outer edge 42a of the blade 42 from the bottom 42z of the notch 42b. The blade thickness is formed so as to gradually increase from the blade thickness L4. In other words, the portion located outside the groove 42t on the negative pressure surface 42q of the blade 42 and the bottom portion 42z of the cutout 42b are smoothly connected by the surface of the groove 42t.

Also in this embodiment, similarly to 1st Embodiment, as shown in FIG. 12, the groove | channel 42t is this groove | channel in the longitudinal direction of the blade | wing 42, ie, the axis of rotation of the blade wheel 41 ( It is formed so that it may become shallow gradually toward both sides from the center part of 42t). In other words, the part corresponding to the groove | channel 42t in the blade | wing 42 is formed so that blade thickness L may become large gradually toward both sides from the center part of the groove | channel 42t. For this reason, in the longitudinal direction of the blade | wing 42, a step is not formed in the boundary part 42e of the groove | channel 42t, and blade | wing thickness L changes continuously.

According to the crossflow fan 4 of this embodiment, the following effects can be acquired.

(5) The blade | wing thickness L4 of the bottom part 42y of the notch 42b was made smaller than the blade | wing thickness L3 of the basic-shaped part 42c. Therefore, the collision loss when the airflow X which flows out from the inner periphery to the impeller 41 flows into the notch 42b can be reduced. As a result, the output of the electric motor which drives the crossflow fan 4 can be reduced compared with the output of the conventional electric motor, and the increase of the output of the electric motor resulting from a notch can be suppressed. .

(6) The portion of the blade 42 corresponding to the groove 42t faces the outer edge 42a of the blade 42 from the bottom 42z of the notch 42b, so that the blade thickness is the blade thickness. It is formed so that it may become large from L gradually. Therefore, the part located outside the groove 42t on the negative pressure surface 42q of the blade 42 and the bottom part 42z of the notch 42b are connected smoothly by the surface of the groove 42t. Therefore, the airflow X which flows in from the inside of the blade | wing 42 to the notch 42b can flow out smoothly out of the vaning wheel 41 along the negative pressure surface 42q. Therefore, the collision loss when the airflow X flows into the notch 42b from the inside of the blade | wing 42 can be reduced. As a result, an increase in the output of the electric motor that drives the crossflow fan 4 can be effectively suppressed due to the formation of cutouts in the blades 42.

(7) The groove 42t is formed so as to gradually become shallow as it faces both sides from the center of this groove 42t in the longitudinal direction of the blade 42, ie, the axis of rotation of the vane 41. In other words, the part corresponding to the groove | channel 42t in the blade | wing 42 is formed so that blade thickness L may become large gradually toward both sides from the center part of the groove | channel 42t. For this reason, in the longitudinal direction of the blade | wing 42, a step is not formed in the boundary part 42e of the groove | channel 42t, and blade | wing thickness L changes continuously. Therefore, compared with the case where the step | step is formed in the boundary part 42e of the groove | channel 42t, the airflow X which flows out from the inside of the blade | wing 42 can be prevented from being scattered, and the crossflow fan 4 is driven. The increase in the output of the electric motor can be further suppressed.

(8) When the pressure surface 42p is in a basic shape, and the groove 42t is formed in the negative pressure surface 42q, a groove corresponding to the notch 42b is formed in the pressure surface 42p. In comparison with this, the pressure given to the air stream X can be increased.

Moreover, in this embodiment, since the air conditioner is equipped with the crossflow fan 4 which can acquire the effect of said (5)-(8), it obtains the same effect as said (5)-(8). Can be.

In addition, this invention is not limited to the said embodiment, It is possible to make various design changes based on the meaning of this invention, and does not exclude them from the scope of this invention. For example, you may change the said embodiment as follows.

In the said 1st and 2nd embodiment, the notch 42b is formed in any one of the outer edge 42a and the inner edge 42d of the blade | wing 42. As shown in FIG. Not only this but notch may be formed in both the outer edge 42a and the inner edge 42d of the blade | wing 42. As shown in FIG. If comprised in this way, since the notch 42b is formed in both the outer edge 42a and the inner edge 42d of the blade | wing 42, noise can be reduced more effectively. In addition, in the suction region N of the crossflow fan 4, the collision loss when the airflow X flows into the notch 42b from the outside of the blade 42 is reduced, and the crossflow fan 4 The collision loss when the airflow X flows into the notch 42b from the inside of the blade 42 in the extraction region M can be reduced. Therefore, compared with the case where the notch 42b is formed only in one of the outer edge 42a and the inner edge 42d, the collision loss can be reduced while reducing the noise more effectively, and the crossflow fan 4 is driven. The increase in the output of the electric motor can be suppressed.

In each said embodiment, the pressure surface 42p is a state with a basic shape, and the groove 42t corresponding to the notch 42b is formed in the negative pressure surface 42q. Not only this but the groove | channel corresponding to the notch 42b may be formed in the pressure surface 42p. By such a structure, since blade | wing thickness L2 (L4) is formed smaller than blade | wing thickness L1 (L3), the effect of said (1)-(3) or (5)-(7) can be acquired.

In each of the above embodiments, the notch 42b is V-shaped, and the blade thickness L gradually decreases as the portion corresponding to the groove 42t in the blade 42 faces both sides from the center portion of the groove 42t. It is formed to be large. Not limited to this, for example, as shown in FIGS. 14 and 15, the spherical notch 42b is formed from the negative pressure surface 42q and the pressure surface 42p of the blade 42 at the outer edge 42a. The groove | channel 42t extended from the outer side of the blade | wing 42 to the inner side may be formed correspondingly to this notch 42b. Sectional views along the 5a-5a line and the 5b-5b line of FIG. 15 are the same as FIG. 5 (a) and FIG. 5 (b), respectively. FIG. 16 is a cross-sectional view taken along line 16-16 of FIG. 15. In this case, the part corresponding to the groove | channel 42t in the blade | wing 42 is not formed so that blade | wing thickness L may become large gradually toward both sides from the center part of the groove | channel 42t, as shown in FIG. A step 42f may be formed in the boundary 42e between the groove 42t and the basic profile portion 42c adjacent to the groove 42t. Even if it is comprised in this way, the effect of said (1) and (2) or (5) and (6) can be acquired. Moreover, the spherical notch 42b may be formed in the inner edge 42d of the blade 42 from the negative pressure surface 42q and the pressure surface 42p.

In each said embodiment, the part corresponding to the groove | channel 42t in the blade | wing 42 is directed toward the inner edge 42d of the blade | wing 42 from the bottom part 42y of the notch 42b. The thickness is formed so as to gradually increase from the blade thickness L. It does not need to be comprised in this way. That is, if the blade thickness L2 or L4 near the bottom part 42y of the notch 42b is formed smaller than the blade thickness L1 of the edge of the base-shaped part 42c, the effect of the said effect (1) or (5) will be performed. You can get it. As described above, the notches 42b may be formed on both the inner and outer edge portions of the blade 42. That is, the notch 42b is formed in the edge part of at least one of both edges of the inner side and the outer side of the blade | wing 42, and the blade thickness of the vicinity of the bottom 42y of the notch 42b is basic shape part 42c. What is necessary is just to form smaller than the thickness of the blade | wing part of the edge part.

In order to suppress the boundary layer of the airflow which flows into the blade | wing 42, the turbulence boundary layer control structure may be provided in the side surface of the blade | wing 42. The turbulent boundary layer control structure is a structure (dimple, groove, rough surface, etc.) which makes the boundary layer transition from laminar flow to turbulent flow. When the turbulent boundary layer control structure is formed, the pressure resistance acting on the blade 42 can be reduced, and the output of the electric motor driving the crossflow fan is reduced as compared with the case where the turbulent boundary layer control structure is not formed. can do. In particular, when the outer edge 42a of the blade 42 is cut off and the cutout is formed in the blade 42, the gas of the flow in which the two-dimensionality is broken (that is, the three-dimensional flow) is the vane 41. In other words, since it flows into the blade 42, turbulent boundary layer control such as dimples or irregular roughness whose cross-sectional shape changes in the directions orthogonal to the rotation axis A1 and the rotation axis A1 (ie, two directions orthogonal to each other). By forming a structure, peeling of the flow of the air which flows into the blade | wing 42 can be suppressed effectively.

For example, as shown in FIG. 17 and FIG. 18, the turbulent boundary layer control which causes the boundary layer of the air flow formed in the vicinity of the negative pressure surface 42q to the negative pressure surface 42q of the blade 42 from laminar flow to turbulent flow. The dimple 42h may be formed as a structure. The dimple 42h has a predetermined depth and has a spherical bottom face. The dimple 42h is formed in the vicinity of the outer edge 42a of the negative pressure surface 42q of the blade 42 along the direction in which air flows. The direction in which air flows in the negative pressure surface 42q of the blade 42 is a direction substantially perpendicular to the rotation axis A1. From the viewpoint of ensuring the depth of the dimple 42h, it is preferable that the dimple 42h is provided in the basic shape part 42c formed between the notches 42b.

19 is a cross-sectional view taken along the 19-19 line in FIG. 18. As illustrated in FIG. 19, when a plurality of dimples 42h are formed along the direction in which air flows on the negative pressure surface 42q of the blade 42, dimples 42j formed to be separated from the outer edge 42a of the blade 42. ) Is preferably formed to have a smaller depth than the dimple 42i formed near the outer edge 42a than the dimple 42j. That is, it is preferable that the depth of the some dimple 42h formed in the vicinity of the outer edge 42a becomes shallow as it goes to the inner edge 42d from the outer edge 42a. Sectional drawing along the 5b-5b line of FIG. 18 is the same as FIG. 5 (b). The blade thickness L of the part in which the dimple 42h was formed in the blade | wing 42 is not contained in the blade thickness L1 of the outer edge 42a of the basic-shaped part 42c. In addition, the "depth of a dimple" here is the maximum depth of the dimple.

As shown in FIG. 18, when three rows of dimples 42h lined up on the rotation axis A1 (that is, the longitudinal direction of the blade 42) are formed, two rows of dimples 42h may have the same depth. do. Specifically, the depth of the third row of dimples 42j formed away from the outer edge 42a among the plurality of dimples 42h is greater than that of the two rows of dimples 42i and 42k formed near the outer edge 42a. It may be made smaller than the depth and formed so that two rows of dimples 42i and 42k may have the same depth. That is, among the plurality of dimples 42h formed in the vicinity of the outer edge 42a, a configuration may be adopted in which only a portion thereof becomes shallower from the outer edge 42a toward the inner edge 42d, and all of these dimples 42h are employed. You may employ | adopt the structure becoming shallow as it goes to the inner side edge 42d from the outer side edge 42a. As shown in Fig. 18, the second row of dimples 42k provided between the dimples 42i in the first row and the dimples 42j in the third row are compared with the second row of dimples 42i and 42j in the rotation axis A1. You may shift by half pitch.

Since the dimple 42h is formed as mentioned above, the boundary layer of the airflow in the vicinity of the negative pressure surface 42q of the blade | wing 42 can transition from laminar flow to turbulent flow. Therefore, the deceleration of the flow of air in the boundary layer is reduced, and as shown by the air flow X in FIG. 20, the flow of air flowing into the vanes 41 (in other words, the vanes 42) is the vanes 42. Peeling from) can be suppressed. As a result, the pressure resistance acting on the blade 42 can be made small, and as shown by the dashed-dotted line in FIG. 21, the cross flow fan is compared with the case where the dimple 42h is not formed (indicated by the solid line). The output of the electric motor to drive can be reduced. In FIG. 20, the broken line has shown the flow of air in the case where the dimple 42h is not formed. FIG. 21 is an airflow-motor output characteristic diagram similar to that of FIG. 8. In Fig. 21, the dashed-dotted line shows the airflow-motor output characteristics for the crossflow fan 4 in which the dimples 42h are formed, and the solid line shows the airflow-motor for the crossflow fan 4 of the first embodiment. The output characteristic is shown, and the dashed-dotted line shows the air volume-motor output characteristic with respect to the conventional cross flow fan 204.

In the case where the turbulent boundary layer control structure is the dimple 42h, the separation effect of the gas flowing into the blade 42 can be made higher than in the case where the turbulent boundary layer control structure is a groove provided extending along the direction in which air flows. . That is, when the turbulent boundary layer control structure is dimple 42h, the shear layer generated at the bottom of the boundary layer can be reduced by transitioning the boundary layer from laminar flow to turbulent flow and generating a secondary flow in the dimple 42h. Therefore, the flow of the air which flows into the blade | wing 42 can be suppressed from peeling from the blade | wing 42 more.

In particular, since the plurality of notches 42b are formed in the blade 42 of the present invention at predetermined intervals, the peeling of the air flow in the dimples 42h is reduced compared with the case where the notches 42b are not formed. The effect can be increased. That is, when the notch 42b is not formed, since the edge portion of the blade is straight and the two-dimensional property of the air flow is strong, when the dimple 42h is formed on the wing where the notch 42b is not formed, , Sufficient peeling reduction effect cannot be obtained. On the other hand, when the notch is formed in the edge part of the blade | wing 42, the air which tries to flow into the vane 41 tends to flow in the notch 42b, and the two-dimensional property of an air flow tends to collapse. Therefore, when dimple 42h is formed in the blade | wing in which the notch 42b is not formed, peeling from the blade | wing 42 of the air flow which two-dimensionality collapsed can be suppressed effectively.

Since the dimple 42h is provided in the basic shape part 42c formed between the notches 42b, compared with the case where the dimple 42h is formed in the groove 42t corresponding to the notches 42b, the desired depth The branches can easily form the dimples 42h. That is, since the blade | wing thickness L of the basic shape part 42c is large compared with the groove | channel 42t, the depth of the dimple 42h can be ensured easily.

Since the depths of the plurality of dimples 42h formed in the vicinity of the outer edge 42a become shallow as they face the inner edge 42d, the dimples 42j formed away from the outer edge 42a of the blade 42 are It has a smaller depth than the dimple 42i formed near the outer edge 42a than the dimple 42j. By varying the depths of the plurality of dimples 42h in this way, the loss due to secondary air flow can be suppressed in the dimples 42j formed away from the outer edge 42a, which has a small effect of suppressing the development of the boundary layer. Can be. Moreover, since the dimple 42j has a small effect of suppressing the development of the boundary layer compared with the dimple 42i formed near the outer edge 42a, the dimple 42j has an effect of suppressing the peeling of air by the plurality of dimples 42h. Is maintained. Therefore, compared with the case where the some dimple 42h has the same depth, the output of the electric motor which drives a crossflow fan can be reduced.

Since the dimple 42h is formed so that the depth of the some dimple 42h formed in the vicinity of the outer edge 42a may become shallow as it goes to the inner edge 42d, the negative pressure of the blade | wing 42 is used using a metal mold | die. It is easy to form a plurality of dimples 42h (that is, dimples 42i, 42j, 42k) along the direction in which air flows on the surface 42q. That is, since the blade 42 is curved, when the plurality of blades 42 are formed using one mold, the dimples 42h are formed when the dies are removed after the blades 42 are formed. In order for the protrusion (not shown) formed in the metal mold to interfere with the blade 42, it may be difficult to remove the mold from the blade 42. Thus, the dimples 42j formed away from the outer edge 42a are formed to have a small depth as compared to the dimples 42i formed near the outer edge 42a, so that the dimples 42j are separated from the outer edge 42a. Can be prevented from interfering with the blades 42 when removing the mold. As a result, the metal mold | die for shaping | molding the blade | wing 42 can be easily peeled off, and using a metal mold | die, a plurality of dimples 42h are formed in the negative pressure surface 42q of the blade | wing 42 along the direction through which air flows. It becomes easy.

Although the case where the dimple 42h was formed in the blade | wing 42 which concerns on 1st Embodiment was demonstrated with reference to drawings, you may form the dimple 42h in any one of the blade | wing 42 of another embodiment mentioned above. .

In the vicinity of the inner edge 42d on the negative pressure surface 42q of the blade 42, a dimple as a turbulent boundary layer control structure may be formed, and both edge portions which are both inner and outer edge portions of the blade 42 are formed. Dimples may be formed in the vicinity.

In the vicinity of the inner edge 42d, when a plurality of dimples are formed along the direction in which air flows on the negative pressure surface 42q of the blade 42, the depths of the plurality of dimples are increased from the inner edge 42d. It is preferable to become shallow as it faces the outer edge 42a. In other words, in the dimples formed in plural in the vicinity of the inner edge 42d, the dimples formed apart from the inner edge 42d are preferably formed to have a small depth as compared to the dimples formed near the outer edge 42a. . That is, when dimples are formed in the vicinity of both edge portions that are both inner and outer edge portions of the blade 42, the depths of the plurality of dimples formed in the vicinity of the outer edge 42a are determined from the outer edge 42a. It is preferable that it becomes shallow as it goes toward the inner edge 42d, and the depth of the some dimple formed in the vicinity of the inner edge 42d becomes shallow as it goes toward the outer edge 42a from the inner edge 42d.

Claims (11)

And a vane comprising a plurality of support plates positioned on a rotation axis of the vane and a plurality of plate-shaped vanes provided on the periphery of the support plate and extending in parallel with the rotation axis, wherein the vane has an outer edge thereof. The side surface which is inclined to be located in the front of the direction of rotation of the vane from the inner edge, and the side surface which is located in the front of the direction of rotation of the vane among both side surfaces of the vane constitutes the pressure surface, and is located at the rear of the rotational direction In the crossflow fan constituting the negative pressure surface,
A plurality of cutouts are formed at predetermined intervals along the rotation axis of the vane at least on one of the inner edge and the outer edge of the wing, and a basic shape is formed between two adjacent cutouts. A cross flow fan, wherein a wing thickness near the bottom is smaller than a wing thickness of the basic shape portion adjacent to the cutout. The method according to claim 1,
The notch is formed at the outer edge of the blade, and a plurality of grooves extending inward from the outside of the blade are formed on either of the pressure surface and the negative pressure surface in correspondence to the notch, so that the bottom of the notch is formed. The wing thickness in the vicinity becomes smaller than the wing thickness of the said basic shape part adjacent to this notch,
Wing thickness of the part corresponding to the said groove | channel in the said wing becomes large gradually as it goes to the inner edge of the said wing from the bottom of the said notch. The method according to claim 1 or 2,
The notch is formed at the inner edge of the blade, and a plurality of grooves extending from the inner side of the blade to the outside on one of the pressure surface and the negative pressure surface are formed in correspondence to the notch, respectively, to thereby form the bottom of the notch. The wing thickness in the vicinity becomes smaller than the wing thickness of the said basic shape part adjacent to this notch,
The cross flow fan of the said blade corresponding to the said groove | channel becomes large gradually as it goes to the outer edge of the said blade from the bottom of the said notch. The method according to claim 1 or 2,
The notch is V-shaped in view of the negative pressure surface and the pressure surface of the blade, and the groove gradually becomes shallow as it goes from the center to both sides in the width direction thereof, and the basic shape adjacent to the groove from the groove. Cross flow fan, characterized in that the blade thickness is continuously changed as it is directed to the portion. The method according to claim 1 or 2,
The said pressure surface is a basic shape as it is, and the said groove | channel is formed in the said negative pressure surface, The cross flow fan characterized by the above-mentioned. The method according to claim 1 or 2,
The negative pressure surface of the blade is provided with a turbulent boundary layer control structure for suppressing separation of the air flow entering the blade from the blade by transitioning the boundary layer of the air flow formed near the negative pressure surface from laminar flow to turbulent flow. Featured Cross Flow Fan. The method of claim 6,
The turbulent boundary layer control structure is provided in the basic shape portion formed between the cutouts. The method of claim 6,
And the turbulent boundary layer control structure is a dimple. The method according to claim 8,
The said dimple is formed in multiple numbers along the direction through which a gas flows in the vicinity of the outer edge of this blade in the negative pressure surface of the said blade,
The depth of the said plurality of dimples becomes shallow as it goes toward the inner edge from the outer edge of the blade. The method according to claim 8,
The said dimple is formed in multiple numbers along the direction through which a gas flows in the vicinity of the inner edge of this blade in the negative pressure surface of the said blade,
The depth of the said plurality of dimples becomes shallow as it goes toward the outer edge from the inner edge of the blade. The air conditioner provided with the crossflow fan of Claim 1 or 2.

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